Example 10.1 A uniform supersonic airflow traveling at Mach 2.0 passes over a wedge M2 (Fig. 10E.1). An oblique shock, making an angle of 40° with the flow Pi 20 kPa direction, is attached to the wedge under these flow conditions. If the static T =-10 °C 0 40% M-2.0 pressure and temperature in the uniform flow are, respectively, 20 kPa and -10 °C, determine the static pressure and temperature behind the wave, the Mach number of the flow passing over the wedge, and the wedge half-angle. Figure 10E.1:

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Example 10.1
A uniform supersonic airflow traveling at Mach 2.0 passes over a wedge
M2
(Fig. 10E.1). An oblique shock, making an angle of 40° with the flow P= 20 kPa
T=-10 °C
0=40%
direction, is attached to the wedge under these flow conditions. If the static
M 2.0
pressure and temperature in the uniform flow are, respectively, 20 kPa and
-10 °C, determine the static pressure and temperature behind the wave, the
Mach number of the flow passing over the wedge, and the wedge half-angle. Figure 10E.1:
Transcribed Image Text:Example 10.1 A uniform supersonic airflow traveling at Mach 2.0 passes over a wedge M2 (Fig. 10E.1). An oblique shock, making an angle of 40° with the flow P= 20 kPa T=-10 °C 0=40% direction, is attached to the wedge under these flow conditions. If the static M 2.0 pressure and temperature in the uniform flow are, respectively, 20 kPa and -10 °C, determine the static pressure and temperature behind the wave, the Mach number of the flow passing over the wedge, and the wedge half-angle. Figure 10E.1:
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